The invention relates to an extruded tile for manufacturing a surface heat exchanger, characterised in that it comprises at least one main structure (12) extending in a main longitudinal direction and forming a substantially planar surface for heat exchange with an outside environment on at least one of its faces, and at least one channel (14a ') for circulating a fluid extending on one of the faces of the main structure in the main longitudinal direction, the tile being configured for a heat exchange between the fluid circulating in the one or more circulation channels (14a') and the outside environment, and for assembly with at least one other extruded tile to form a surface heat exchanger. The invention also relates to a surface heat exchanger comprising a plurality of extruded tiles, to a method for manufacturing an extruded tile and to a method for manufacturing an exchanger.
F28F 1/02 - Tubular elements of cross-section which is non-circular
F28D 1/02 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid
F28D 1/03 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits
The invention relates to an actuator of an electric equipment for regulating a flow of fluid in a conduit comprising a housing (44), an electric motor (10), a concentric, reversible, planetary reducing gear housed in said housing and mechanically connected to said motor and comprising a first reducing stage and a second reducing stage comprising at least one planet gear (31, 32, 33) with superposed outer double toothing, said top toothing (31a) being engaged with a fixed ring gear (34) and said bottom toothing (31b) being engaged with a mobile ring gear (35), and a concentric torsion spring (42) arranged around said mobile ring gear (35), mechanically connected to the housing (44) and to the mobile ring gear (35), and configured to be able to spontaneously cause the movement of said mobile ring gear (35) and of an output shaft (40) into a predetermined position in the event of a loss of electric power supply of said electric motor (10).
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
3.
A COMPRESSOR ARRANGEMENT FOR A VEHICLE FUEL CELL SYSTEM
pppEERR). It is suggested that the second compressor stage (5) comprises a dual-flow compressor device (14), said compressor device (14) having two compressor wheels (14a, 14b) operatively coupled to a common second-stage drive shaft (14c).
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
4.
Device for Filtering Air Intended to Supply An Air System Of A Transport Vehicle System Comprising Such Device And Method For Manufacturing Such A Filtering Device
SAINT-GOBAIN CENTRE DE RECHERCHES ET D'ETUDES EUROPEEN (France)
Inventor
Heraud, Phillippe
Creibine, Lamia
Jacquart, Jerome
Nguyen Van Nuci, Patrick
Giardella, Lucas
Abstract
Device (50) for filtering air intended to supply an air system of an airborne, rail-bound or automotive transport vehicle, characterized in that it comprises a porous three-dimensional structure (52) comprising at least one portion intended to be in contact with said air to be filtered, referred to as exchange portion (53), said exchange portion (53) comprising at least one adsorbent material in the form of particles selected from carbon, a zeolite, a metal organic framework and mixtures thereof, said adsorbent particles being bound by a binder, said binder comprising at least one material selected from the group formed of boehmite, hydrated aluminas, transition aluminas and mixtures thereof.
B01D 53/04 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography with stationary adsorbents
B01D 29/00 - Filters with filtering elements stationary during filtration, e.g. pressure or suction filters, not covered by groups Filtering elements therefor
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
5.
HEAT EXCHANGER COMPRISING AT LEAST ONE PLATE THAT COMPRISES AT LEAST ONE WATER SPRAY CHANNEL, A COOLING SYSTEM, AND A MANUFACTURING METHOD THEREOF
The invention relates to a heat exchanger comprising: a flow enclosure that comprises a first inlet (2) and a first outlet (4) for a first fluid, a second inlet (6) and a second outlet (8) for a second fluid outside the flow enclosure, characterised in that the exchanger comprises a plurality of plates (20, 25) for the flow of the first fluid that are arranged substantially parallel to one another, wherein each space between two plates (20, 25) defines a layer for the flow of the second fluid, and wherein each plate (20, 25) comprises: - a plurality of ducts (21) configured to allow the first fluid to flow between the first inlet (2) and the first outlet (4), wherein at least one water flow channel (17), has at least one inlet (22) and a plurality of spray apertures (26), which are configured to be able to open and make contact with the second fluid.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 9/02 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the heat-exchange media travelling at an angle to one another
6.
HEAT EXCHANGER COMPRISING AT LEAST ONE LATERAL ENCASULATION PLATE, AIR CONDITIONING SYSTEM AND VEHICLE
The invention relates to a plate heat exchanger (1) configured for a heat exchange between a first fluid flowing in a first pass and a second fluid flowing in a second pass, the fluids flowing between two external plates (2), comprising a plate exchanger block comprising a plurality of internal plates (12, 14) arranged substantially in parallel with each other, said internal plates being arranged substantially in parallel with the external plates (2),
The invention relates to a plate heat exchanger (1) configured for a heat exchange between a first fluid flowing in a first pass and a second fluid flowing in a second pass, the fluids flowing between two external plates (2), comprising a plate exchanger block comprising a plurality of internal plates (12, 14) arranged substantially in parallel with each other, said internal plates being arranged substantially in parallel with the external plates (2),
characterized in that it comprises at least one lateral encapsulation plate (20) extending substantially orthogonally to said internal plates, each lateral encapsulation plate being fixed in contact with said external plates (2) so as to laterally close said second pass.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
7.
HEAT-EXCHANGE DEVICE COMPRISING FLOW LIMITING DEVICES, AIR-CONDITIONING SYSTEM AND VEHICLE
The invention relates to a heat-exchange device comprising:
an exchanger block (12) disposed in a flow enclosure defined by two external plates,
said exchanger block comprising a first internal layer and a last internal layer allowing the flow of the first heat-transfer fluid, said exchanger block comprising a plurality of internal plates (13, 14, 15, 16) disposed substantially in parallel with each other between two ends of said exchanger block,
characterized in that each first internal layer and each last internal layer comprises at least one flow limiting device (20) configured to be able to impede, at least in part, the flow of said first stream of fluid in said internal layer.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
8.
HEAT EXCHANGE DEVICE COMPRISING AT LEAST ONE MANIFOLD, AND AIR CONDITIONING SYSTEM AND VEHICLE
The invention relates to a heat exchange device comprising: a heat exchange matrix (50) accommodated in a circulation enclosure and formed of a plurality of heat exchange pipes, each pipe comprising at least one duct extending mainly in a longitudinal direction, each duct at least partially defining a flow channel for a second heat transfer fluid, at least one manifold (20) comprising at least one duct portion (22, 23, 24) extending mainly in a plane orthogonal to the longitudinal direction, the manifold comprising a plurality of ports (30), at least one fluid distribution header (40) configured to allow a second heat transfer fluid to flow between at least one port of the manifold and at least one duct, each port of the manifold opening into a distribution header. The invention relates to an air conditioning system and to an aircraft comprising such a heat exchange device.
The invention relates to an aircraft pylon comprising a cooling exchanger (10) with counterflow of a flow of hot primary air (22) by a flow of cold secondary air (24) flowing oppositely to each other in a longitudinal direction (L), characterized in that it comprises two bundles (10a, 10b) juxtaposed on both sides of a central axis (12) and each comprising a plurality of parallel longitudinal plates (15) forming a hot pass and a cold pass of the bundle, and in that one of the hot or cold passes of each bundle is supplied by a central inlet (14a) common to the two bundles (10a, 10b) and one of the hot or cold passes of each bundle opens into a central outlet (16) common to the two bundles, said inlets (14b, 14c) and outlets (16b, 16c) of the conjugate passes, referred to as side inlets and outlets, being separate and diverging laterally from said central axis (12).
B64D 27/40 - Arrangements for mounting power plants in aircraft
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
10.
METHOD FOR MANUFACTURING A HEAT EXCHANGER BY COLD GAS DYNAMIC SPRAYING AND ASSOCIATED HEAT EXCHANGER
The invention relates to a method for manufacturing a heat exchanger comprising at least one tube (12) for circulating a fluid and configured to allow heat exchange between the fluid circulating through each tube (12) and a profile surrounding each tube, characterised in that it comprises a step of cold gas dynamic spraying of metal powder onto each tube (12) arranged in a first mould so as to form a first profile portion (14a), and a step of cold gas dynamic spraying of metal powder onto each tube (12) arranged in a second mould (16b) so as to form a second profile portion (14b).
The invention relates to a fluid system of an aircraft comprising at least one flow conduit for a fluid, at least one electric valve (30, 40, 50) for regulating the flow of fluid in said fluid conduit by movement of a regulating member in said fluid conduit, a central computer (20) configured to be able to issue control instructions to each electric regulating valve (30, 40, 50) depending on the in-flight conditions of said aircraft, and an electric circuit (60) for powering said computer and each electric regulating valve, characterized in that at least one electric regulating valve, referred to as smart valve, is equipped with an integrated actuator connected to the central computer and/or to another smart valve of the fluid system by at least one multiplexed data communications bus (22, 24, 42, 44).
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
12.
DEVICE FOR SUPPLYING A PLURALITY OF CATHODES OF A FUEL SYSTEM
The invention relates to a supply device for compressed air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of compressed air to all of the cathodes (100a-100d), a group of ducts configured to conduct the compressed air to each cathode (100a-100d), for each cathode (100a-100d), a proportioning valve (20a-20d) upstream or downstream of said cathode (100a-100d) which is configured to regulate the flow rate of compressed air passing through said cathode (100a-100d), anti-pumping protection means (30, 32) configured to allow the flow of a minimum flow rate of compressed air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportioning valve (20a-20d) and/or the operation of the anti-pumping protection means (30, 32).
The invention relates to a method for installing coil groups in an electric machine (100), each coil group (104, 204) comprising at least one coil, each coil being composed of a plurality of turns of conductors, characterized in that it comprises, for each coil group (104, 204), the following installation steps applied to each coil group before being applied to the following coil group: a step of inserting a first coil group into at least two free or partially occupied slots (106) of the electric machine (100), the coil portions arranged outside the slots forming the coil heads, a definitive shaping step by compacting the heads of the coils of said coil group into a predetermined shape, by a preconfigured apparatus.
H02K 15/00 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
H02K 3/38 - Windings characterised by the shape, form or construction of the insulation around winding heads, equalising connectors, or connections thereto
H02K 15/10 - Applying solid insulation to windings, stators or rotors, e.g. applying insulating tapes
14.
HEAT EXCHANGER WITH A CLOSING BAR OPTIMIZED FOR PROTECTION AGAINST ICING
Heat exchanger with plates, which is configured for a heat exchange between a hot fluid and a cold fluid, comprising at least one core band (130a, 130b) arranged in order to maintain the sealing tightness, a plurality of closing bars (138) defining, with the closing plates, flow channels, characterized in that the core band (130a) arranged at a cold pass inlet and at a hot pass inlet comprises an inlet (132) for supplying hot air, and in that at least one closing bar (138) arranged in the lengthwise direction of the inlet of the cold pass comprises an inlet for said hot air and a flow circuit for said hot air in a U shape and comprising two sections, each extending over the whole length of the closing bar, a hot air outlet for expelling the hot air in the hot pass, and an intermediate section forming the base of the U.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
Described herein is the location of an air leak in a network for supplying pressurized air that includes one or more components and at least one leak detection loop including one or more sensing elements. The location includes receiving information representative of detection of the leak by a sensing element of the detection loop, receiving a 3D model of at least part of the network for supplying pressurized air, interrogating a database associating a leak site of a component with each location on the detection loop, determining a precise location of the leak on the network for supplying pressurized air, mapping the precise location relative to a component, and instructing display of the 3D model corresponding to the component of the supply network and of the precise location.
G01M 3/04 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
G06F 30/18 - Network design, e.g. design based on topological or interconnect aspects of utility systems, piping, heating ventilation air conditioning [HVAC] or cabling
16.
HEAT EXCHANGER WITH A FLUID FLOW TUBE AND PROTECTION AGAINST MICROMETEORITES
A heat exchanger includes a fluid flow tube configured to allow an exchange of heat between the fluid flowing in the tube and an enclosure surrounding the tube. The enclosure is formed from two profiled bars configured to surround the tube over at least one part of its length. Each of the bars includes a recess adapted to receive the tube, and a joint surface configured to form a joint with the other profiled bar. The joint surfaces of the profiled bars form a gap therebetween. As well, the joint surfaces of the profiled bars are arranged in different planes such that the gap forms at least one baffle on each side of the tube.
B23K 1/00 - Soldering, e.g. brazing, or unsoldering
F28F 1/20 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally the means being attachable to the element
F28F 21/08 - Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
17.
SYSTEM AND METHOD FOR COOLING A FUEL CELL ASSEMBLY
The invention relates to a system for cooling a fuel cell assembly (10) of a transport vehicle, such as an aircraft, comprising: a cooling fluid circulation loop (20); a cooling heat exchanger (24) configured to be able to provide heat exchanges between said loop (20) and a channel (25) for circulating cooling air (26); a variable-speed pump (21) for supplying said cooling loop with cooling fluid as a function of a measurement representative of the cooling need of said fuel cell assembly; for each fuel cell (10a, 10b, 10c) of said cell assembly, a 3-way valve (12a, 12b, 12c) for regulating the flow rate of cooling fluid supplying this cell as a function of a measurement representative of the cooling need of this cell.
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
18.
MODULE FOR SUPPLYING PRESSURIZED FRESH AIR TO AN AIR-CONDITIONING PACK OF AN AIRCRAFT CABIN, AIR-CONDITIONING SYSTEM EQUIPPED WITH SUCH A MODULE, AND CORRESPONDING METHOD
The invention relates to an air-conditioning system for an aircraft cabin (5) comprising: an engine air bleed device (10); an air-conditioning pack (20) comprising a pack air inlet (21) connected to said engine bleed device (10), and a pack air outlet (22) connected to said cabin (5); an auxiliary module (50) for supplying pressurized air comprising an auxiliary turbomachine (51), comprising a compressor (52) supplied with external fresh air and a turbine suitable to be able to be supplied with air coming from the engine bleed device; and a control unit configured to activate either a standard mode in which the pack air inlet is supplied with the pressurized air coming from the engine bleed device (10), or a fresh air mode in which said pack air inlet (21) is supplied with the pressurized air coming from the auxiliary module (50).
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
19.
System for providing protection from icing using a fuel cell
b), and two liquid-liquid heat exchangers (116, 216) in which the cooling liquids form a hot pass and the icing protection liquids form a cold pass to reheat the icing protection liquid by the heat from the cooling liquids.
The invention relates to a profiled part (12) for a heat exchanger, configured to have at least one fluid flow tube (14) passing through it, comprising, for each flow tube (14), a hollow cylinder (18) comprising an inner surface configured to receive said flow tube (14), the cylinder (18) having an inner diameter which is substantially equal to the outer diameter of said flow tube (14). The profiled part (12) is characterized in that the profiled part comprises a slit (16) extending over the whole length of the cylinder (18) and configured to permit, by application of at least one mechanical force to the profiled part, a modification in the inner diameter of the cylinder (18) in order respectively to permit the insertion of the tube into the cylinder (18) or the clamping of the tube (14) by the inner surface of the cylinder (18). The invention also relates to a heat exchanger (10) comprising such a profiled part (12) and a flow tube (14).
F28F 1/20 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally the means being attachable to the element
21.
VIBRATION ABSORBING DEVICE WITH A WEIGHTED MEMBRANE ANO FLUID DISPLACEMENT
INSTITUT SUPÉRIEUR DE L'AÉRONAUTIQUE ET DE L'ESPACE (France)
Inventor
Roncen, Thomas
Manet, Vincent
Michon, Guilhem
Abstract
Vibration absorbing device comprising a housing (12), a membrane (14) enclosed in the housing (12) and thus forming two chambers (18a, 18b) in the housing (12), said chambers (18a, 18b) being filled with a fluid, at least one weight (16), arranged on the membrane (14) in order that a movement of the weight (16) causes a movement of the membrane (14), and at least one duct (24) arranged to permit the fluid to flow between the two chambers (18a, 18b) if the membrane (14) and the weight (16) move.
A heat-exchange device includes a flow enclosure defined by two external plates, a first inlet and a first outlet for a first heat-transfer fluid, a second inlet and a second outlet for a second heat-transfer fluid, and an exchanger block with plates disposed in the flow enclosure so as to be in fluid communication with the inlets and outlets in order to permit the flow of the first fluid and of the second fluid into and through this exchanger block and the transfer of calories therebetween. Each external plate has at least one hollow. An air-conditioning system may include such device and an aircraft, in turn, can include such air-conditioning system.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F24F 13/30 - Arrangement or mounting of heat-exchangers
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
23.
DEVICE FOR SUPPLYING PRESSURISED AIR TO A FUEL CELL CATHODE, WITH OPTIMISED COOLING
Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26).
Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26).
The device is characterised in that it comprises a cooling channel (32) configured to receive at least some of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
H02K 5/18 - Casings or enclosures characterised by the shape, form or construction thereof with ribs or fins for improving heat transfer
24.
Driven turbocompressor of an air conditioning system having optimized cooling
The invention relates to a driven turbocompressor of an air conditioning system, comprising a compressor (12) which is connected to an air intake duct (14) and to an inlet (112) of a cabin of a vehicle, and is configured to receive air from the air intake duct (14), to compress it and to provide it to the cabin, a motor (16) that is configured to drive the compressor (12) and is surrounded by a casing (18), a recovery turbine (26) that is configured to expand the cabin air (24) coming from an outlet (114) of the cabin. The device is characterized in that it comprises a cooling duct (32) configured to receive at least part of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
The invention relates to a plate heat exchanger (1), configured for exchanging heat between a first fluid flowing through a first duct and a second fluid flowing through a second duct, wherein the fluids flow between two external plates (2), which plate heat exchanger comprises a plate exchanger unit comprising a plurality of internal plates (12, 14) that are arranged substantially parallel to one another, the internal plates being arranged substantially parallel to the external plates (2) and characterised in that it comprises at least one lateral encapsulation plate (20) extending substantially orthogonally to the internal plates, each lateral encapsulation plate being contactedly attached to the external plates (2) so as to laterally close the second duct.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F28F 9/00 - CasingsHeader boxesAuxiliary supports for elementsAuxiliary members within casings
26.
HEAT-EXCHANGE DEVICE COMPRISING FLOW-LIMITING DEVICES, AIR-CONDITIONING SYSTEM AND VEHICLE
The invention relates to a heat-exchange device comprising: an exchanger block (12) arranged in a circulation chamber bounded by two external plates, said exchanger block comprising a first internal layer and a last internal layer allowing the circulation of the first heat-transfer fluid, said exchanger block comprising a plurality of internal plates (13, 14, 15, 16) arranged substantially in parallel with one another between two ends of said exchanger block, characterised in that each first internal layer and each last internal layer comprises at least one flow-limiting device (20) that is configured to be able to impede at least in part the circulation of said first fluid flow in said internal layer.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
The invention relates to a system for cooling a fuel cell (10) of a transport vehicle such as an aircraft, comprising: a cooling heat exchanger (30) configured to be able to exchange heat between a loop (20) for cooling the cell and a channel for circulating dynamic air; a device (22, 23) for recovering water produced by said fuel cell; a tank (25) for storing recovered water; a device (50) for spraying water into said dynamic air channel (40) upstream of said heat exchanger (30); and a computer (28) for controlling the amount of sprayed water on the basis of a measurement representing the temperature of said fuel cell (10).
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04992 - Processes for controlling fuel cells or fuel cell systems characterised by the implementation of mathematical or computational algorithms, e.g. feedback control loops, fuzzy logic, neural networks or artificial intelligence
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
characterized in that each plate extends along a non-planar surface following at least a first oscillating curve, and each fin further following at least one second oscillating curve along at least one second main direction, in such a way that each passage path allows the fluid to flow in the closed space along a fluid direction defined by a generatrix that is a combination at least of the first oscillating curve and the second oscillating curve.
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/06 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being attachable to the element
29.
AIRCRAFT ENGINE SUSPENSION PYLON PROVIDED WITH A COUNTERFLOW COOLING EXCHANGER
The invention relates to an aircraft pylon comprising a counterflow cooling exchanger (10) for cooling a stream of hot primary air (22) by a stream of cold secondary air (24) flowing in opposite directions to one another in a longitudinal direction (L), characterised in that it comprises two bundles (10a, 10b) juxtaposed on either side of a central axis (12) and each comprising a plurality of longitudinal parallel plates (15) which form a hot pass and a cold pass of the bundle, and in that one of the hot or cold passes of each bundle is fed by a central inlet (14a) common to the two bundles (10a, 10b) and one of the hot or cold passes of each bundle opens into a central outlet (16) common to the two bundles, said inlets (14b, 14c) and outlets (16b, 16c) of the combined passes, referred to as lateral inlets and outlets, being separated and diverging laterally from said central axis (12).
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
30.
Air conditioning system for a cabin of an air or rail transport vehicle using a pneumatic and thermal air source which is separate from the air conditioning source
b) of said power turbine (4) and said ram-air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a thermal energy source for said ram air being supplied to said primary circuit of said primary exchanger (PHX).
Method for manufacturing a fire-resistant part of an air conditioning system for an air or rail transport vehicle, characterized in that it includes at least the following steps: a step of obtaining a part including at least one aluminum alloy surface portion, and a step of treating the aluminum alloy surface portion by use of micro-arc oxidation in order to produce a ceramic coating on the surface portion.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F16K 25/00 - Details relating to contact between valve members and seats
The invention relates to an electrical air conditioning system for air conditioning a cabin (10) of an aircraft comprising a source (11) of fresh air, a dynamic air circulation duct (12), a motorized compressor (13) comprising an air inlet connected to said source of fresh air, and an air outlet connected to a primary cooling exchanger (PHx) housed in said dynamic air duct; an air cycle turbomachine (14) comprising at least a first compressor (15) and a first turbine (17) that are mechanically coupled to one another, said first compressor comprising an air inlet that can be connected either to said primary cooling exchanger (PHx) or to said source (11) of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine (17) comprising an air inlet that can be connected either to a discharge port (54) for discharging stale air from said cabin or to said main cooling exchanger (MHx), and an air outlet that can be connected either to said cabin (10) or to an air injector (52) opening into said dynamic air duct.
Heat exchanger assembly comprising a ram air flow channel (14) extending in a longitudinal direction, and characterized in that said assembly comprises: at least two separate heat exchangers (12a, 12b) that are adjacent in a transverse direction perpendicular to the longitudinal direction, are arranged in the ram air flow channel (14), and are configured such that the ram air passing through said channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through said heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured for the passage therethrough of a fluid that is intended to be cooled and that forms a hot pass (20a, 20b); and an air passage which is provided between the heat exchangers and forms a thermally insulating air gap (18) between said exchangers (12a, 12b), and through which the ram air flows, said air passage extending in said longitudinal direction of said ram air flow channel (14).
The invention relates to a method for installing coil groups in an electric machine (100), each coil group (104, 204) comprising at least one coil, each coil being composed of a plurality of turns of conductors, characterised in that it comprises, for each coil group (104, 204), the following installation steps applied to each coil group before being applied to the following coil group: a step of inserting a first coil group into at least two free or partially occupied slots (106) of the electric machine (100), the coil portions arranged outside the slots forming the coil heads, and a final shaping step in which the heads of the coils of said coil group are compacted into a predetermined shape, by a preconfigured tool.
H02K 3/38 - Windings characterised by the shape, form or construction of the insulation around winding heads, equalising connectors, or connections thereto
H02K 15/00 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
H02K 15/10 - Applying solid insulation to windings, stators or rotors, e.g. applying insulating tapes
35.
DEVICE FOR SUPPLYING A PLURALITY OF CATHODES OF A FUEL CELL SYSTEM
The invention relates to a device for supplying pressurized air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of pressurized air to all the cathodes (100a-100d), a set of ducts configured to duct the pressurized air towards each cathode (100a-100d), for each cathode (100a-100d), a proportional valve (20a-20d) upstream or downstream of said cathode (100a-100d) and configured to regulate the flow rate of pressurized air passing through said cathode (100a-100d), anti-surge protection means (30, 32) configured to allow the circulation of a minimal flow rate of pressurized air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportional valve (20a-20d) and/or the operation of the anti-surge protection means (30, 32).
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
A method and a system are provided for monitoring the state of a heat exchanger (17) in an air circuit (5) of an aircraft (7), the heat exchanger being intended to cool the air extracted from a source of a main hot air source of the aircraft. An acquisition module (11) is configured to acquire temperature measurements taken by a probe disposed at an outlet of said heat exchanger, the acquisition being carried out when the air circuit is supplied by a secondary hot air source downstream of the heat exchanger and the main hot air source being turned off. A processor (9) is configured to select a relevant temperature measurement from the temperature measurements and to detect a possible leak in the heat exchanger (17) by comparing the relevant temperature measurement to a predetermined alert threshold.
G01M 3/00 - Investigating fluid tightness of structures
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64F 5/60 - Testing or inspecting aircraft components or systems
The invention relates to a regulator, configured to receive a stream of hot air carrying pneumatic power via an air inlet (12), to treat this hot air and to send the treated hot air to an air outlet (14) configured 5 to supply a pneumatic actuator (16), comprising a reference pressure source and an air expansion device comprising a diaphragm (22), the diaphragm (22) being configured to control the flow rate of the hot air stream by comparing the pressure of said hot air stream with the reference pressure of the reference pressure source. The regulator is characterized in that it 10 comprises an air intake (24) configured to receive a cold source, and a pipe (25) for guiding the cold source to the diaphragm (22), so that the cold source forms the reference pressure source and a source for cooling the diaphragm (22).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F25B 9/00 - Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
39.
Heat exchanger of an air-conditioning system of a cabin of an aircraft, and system comprising such a heat exchanger
Heat exchanger of an air-conditioning system of a cabin of a transport vehicle, comprising: a primary circuit supplied by a first air flow, a secondary circuit supplied by a second air flow, a casing defining an air-circulation enclosure, a primary circuit inlet box allowing entry into said air-circulation enclosure, and a primary circuit outlet box allowing exit from the air-circulation enclosure, characterized in that said inlet box is mounted removably on said casing, and in that it houses a three-dimensional structure forming a catalytic and/or adsorbent support for treating the air of said primary circuit, and a means for distributing said first air flow into said heat-exchange matrix.
Air conditioning system for a cabin of an air or rail transport vehicle, comprising: a pneumatic turbine engine that comprises at least one compressor and at least one turbine (126) and is connected by a mechanical shaft extending along an axis, referred to as the turbine engine axis (132), said turbine comprising an air inlet and an air outlet; and a water extraction loop that comprises a heater (110), a condenser (112) and a water separator (114), is fluidically arranged between an air outlet of the compressor and the air inlet of said turbine (126), and is configured to dry the air supplied to said turbine (126), characterized in that said heater (110), said condenser (112), and said water separator (114) are arranged in series on the turbine engine axis (132) or around said axis, forming the air inlet of said turbine (126).
The invention relates to a regulator, configured to receive a hot air flow via an air inlet (12), to treat this hot air and to transmit the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising at least one temperature-sensitive electrical and/or mechanical element (36, 37), and a regulator body (100). The regulator is characterized in that the regulator body is composed of a heat-conducting hollow enclosure (28) at least partially surrounding a duct (22) for transporting the hot air flow, said cavity being at least partially filled with a metal mesh produced by additive manufacturing that allows the cooling air to circulate, and in that the temperature-sensitive electrical and/or mechanical element (36, 37) is arranged in, or in contact with, the regulator so as to be cooled by the cooling air by thermal conduction.
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F16K 49/00 - Means in or on valves for heating or cooling
B33Y 80/00 - Products made by additive manufacturing
42.
DISTRIBUTED PNEUMATIC SUPPLY SYSTEM OF AN AIRCRAFT
The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
The invention relates to an air conditioning system for an aircraft cabin, comprising two motorized turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, called cooling turbine (16b), helping cool the air.
The invention relates to an air conditioning system for an aircraft cabin, comprising two motorized turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, called cooling turbine (16b), helping cool the air.
The air conditioning system comprises a network of pipes and associated valves, connected to the common outlet (24) of the compressors and making it possible to supply, from the common outlet of the compressors:
either the inlet (160) of the water extraction turbine (16a), or the inlet (164) of the cooling turbine (16b), bypassing the turbine (16a) and the water extraction loop,
or an outlet (60) of the air conditioning system directly, bypassing the cooling turbine (16b) and the water extraction turbine (16a).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
44.
HEAT EXCHANGER WITH CLOSING BAR OPTIMISED FOR ICE PROTECTION
Disclosed is a plate heat exchanger, for heat exchange between a hot fluid and a cold fluid, comprising at least one bundle edge (130a, 130b) for maintaining the sealing, a plurality of closure bars (138) defining, with the closure plates, flow channels, characterised in that the bundle edge (130a) arranged at a cold pass inlet and a hot pass inlet comprises a hot air supply inlet (132), and in that at least one closure bar (138) arranged in the length of the cold pass inlet comprises an inlet for the hot air and a flow circuit for the hot air that is a U-shaped and comprises two sections each extending over the entire length of the closure bar, a hot air outlet for rejecting the hot air in the hot pass, and an intermediate section forming the base of the U.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
45.
Air conditioning system equipped with a system for the thermal management of oil and of pressurized air
d) designed to provide heat exchanges between a second oil circuit (28) and the flow air (206; 208), allowing the heat from said second oil circuit (26) to be transferred to the flow air (206; 208); and at least one circuit (30) connecting the first oil circuit (26) and said second oil circuit (28).
The invention relates to a system for cooling a fuel cell assembly (10) of a transport vehicle, such as an aircraft, comprising: a coolant circulation loop (20); a cooling heat exchanger (24) configured to be able to provide heat exchanges between said loop (20) and a channel (25) for circulating a cooling air (26); a variable-speed pump (21) for supplying said cooling loop with coolant as a function of a measurement representative of the cooling need of said fuel cell assembly; for each fuel cell (10a, 10b, 10c) of said cell assembly, a 3-way valve (12a, 12b, 12c) for regulating the flow rate of coolant supplying this cell as a function of a measurement representative of the cooling need of this cell.
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
47.
DEVICE FOR FILTERING AIR INTENDED TO SUPPLY AN AIR SYSTEM OF A TRANSPORT VEHICLE, SYSTEM COMPRISING SUCH A DEVICE, AND METHOD FOR MANUFACTURING SUCH A FILTERING DEVICE
SAINT-GOBAIN CENTRE DE RECHERCHES ET D'ETUDES EUROPEEN (France)
Inventor
Héraud, Philippe
Dreibine, Lamia
Jacquart, Jérôme
Nguyen Van Nuoi, Patrick
Giardella, Lucas
Abstract
Device (50) for filtering air intended to supply an air system of an air-transport vehicle, rail vehicle or motor vehicle, characterized in that it comprises a porous three-dimensional structure (52) comprising at least one portion intended to be in contact with said air to be filtered, termed exchange portion (53), said exchange portion (53) comprising at least one adsorbent material in the form of particles chosen from carbon, a zeolite, a metal organic framework and mixtures thereof, said adsorbent particles being connected by a binder, said binder comprising at least one material chosen from the group consisting of boehmite, hydrated aluminas, transition aluminas and mixtures thereof.
B01D 53/04 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography with stationary adsorbents
B01J 20/20 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising inorganic material comprising free carbonSolid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising inorganic material comprising carbon obtained by carbonising processes
B01J 20/22 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising organic material
B01J 20/28 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof characterised by their form or physical properties
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B01J 20/30 - Processes for preparing, regenerating or reactivating
MODULE FOR SUPPLYING PRESSURISED FRESH AIR TO AN AIR-CONDITIONING PACK OF AN AIRCRAFT CABIN, AIR-CONDITIONING SYSTEM EQUIPPED WITH SUCH A MODULE AND CORRESPONDING METHOD
The invention relates to an air conditioning system for an aircraft cabin (5), comprising: an engine air bleed device (10); an air conditioning pack (20) comprising a pack air inlet (21) connected to the engine bleed device (10), and a pack air outlet (22) connected to the cabin (5); an auxiliary module (50) for supplying pressurised air comprising an auxiliary turbomachine (51) comprising a compressor (52) supplied with outside fresh air and a turbine capable of being supplied with air originating from the engine bleed device; and a control unit configured to activate either a standard mode in which the pack air inlet is supplied with pressurised air originating from the engine bleed device (10), or a fresh air mode in which the pack air inlet (21) is supplied with pressurised air originating from the auxiliary module (50).
Disclosed is a system for protecting an outer surface of an aircraft from icing, comprising at least two fuel cells (112, 212), characterised in that it comprises a first and a third liquid circuit (114, 214) each circulating a coolant for cooling the fuel cells (112, 212), a second and a fourth liquid circuit (118a, 118b) each circulating an anti-icing liquid, at least two anti-icing heat exchangers (120a-d, 220a-d) arranged on the outer surface of the aircraft and passed through by each anti-icing liquid when it circulates in the second or the fourth liquid circuit (118a, 118b), and two liquid-liquid heat exchangers (116, 216) in which the coolants form a hot pass and the icing-protection liquids form a cold pass in order to warm the icing-protection liquid by the heat of the coolant.
INSTITUT SUPERIEUR DE L'AERONAUTIQUE ET DE L'ESPACE (France)
Inventor
Roncen, Thomas
Manet, Vincent
Michon, Guilhem
Abstract
Vibration absorbing device comprising a housing (12), a membrane (14) embedded in the housing (12) and thus forming two chambers (18a, 18b) in the housing (12), the chambers (18a, 18b) being filled with a fluid, at least one weight (16) arranged on the membrane (14) such that a movement of the weight (16) causes a movement of the membrane (14), and at least one duct (24) arranged to allow the fluid to flow between the two chambers (18a, 18b) in the event of movement of the membrane (14) and the weight (16).
Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger.
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
52.
Device for cooling heat-sensitive control members of a pneumatic or electropneumatic valve, and valve equipped with such a cooling device
The invention relates to a device (30) for cooling heat-sensitive control members (29) of a pneumatic or electropneumatic valve (20), comprising a containment casing (31) designed to contain said control members (29): a fresh air inlet (32) in said containment casing (31); an air outlet (33) of said containment casing, provided with a ventilation air tube (34) that comprises: an air acceleration column (35) which puts into fluidic communication said containment casing (31) and the air outlet (33); a primary supply (37) for supplying the acceleration column (35) with primary air; a secondary supply (38) for supplying the acceleration column (35) with secondary air, provided in said containment casing (31) such that the primary air can drive and accelerate the secondary air in the direction of the air outlet so as to produce forced air ventilation in said containment casing (31) between the air inlet (32) and the air outlet (33).
F16K 49/00 - Means in or on valves for heating or cooling
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
53.
Distributor for a turbomachine radial turbine, turbomachine comprising such a distributor and air conditioning system comprising such a turbomachine
The invention relates to a distributor for a turbomachine radial turbine, comprising an annular grill (26) extending about a central axis (10) and comprising a plurality of variable-pitch blades (31), defining between them an air passage cross section, characterized in that each blade is rotatably mounted about a pivot shaft (32), itself moveable in a translation direction, comprising at least one radial component, such that said blade may, upon actuation of control means (40), be pivoted about the pivot shaft and/or moved in relation to the central axis in said translation direction so as to be able to modify the air passage cross section by respectively controlling the metal angle (α3) and the radial spacing (ΔR).
F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F04D 29/46 - Fluid-guiding means, e.g. diffusers adjustable
54.
Air conditioning system for an aircraft cabin, comprising means for reheating the water collected by the water extraction loop
Air conditioning system for a cabin (10) of an aircraft, comprising: an air bleed device; an air cycle turbine engine (12); at least one main cooling exchanger (16); a water extraction loop (30); and a pipe (26) for distributing water extracted by said extraction loop (30), characterized in that said system further comprises means (40) for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel (22) which supplies said main exchanger (16).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26). The device is characterised in that it comprises a cooling channel (32) configured to receive at least some of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
56.
DRIVEN TURBOCOMPRESSOR OF AN AIR CONDITIONING SYSTEM, HAVING OPTIMIZED COOLING
The invention relates to a driven turbocompressor of an air conditioning system, comprising a compressor (12) which is connected to an air intake duct (14) and to an inlet (112) of a cabin of a vehicle, and is configured to receive air from the air intake duct (14), to compress it and to provide it to the cabin, a motor (16) that is configured to drive the compressor (12) and is surrounded by a casing (18), a recovery turbine (26) that is configured to expand the cabin air (24) coming from an outlet (114) of the cabin. The device is characterized in that it comprises a cooling duct (32) configured to receive at least part of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
d), and suitable for being able to be supplied with a third fluid, referred to as intermediate fluid, brought to a third temperature, different from said first temperature.
F28D 7/10 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
58.
Loop for extracting water from an air conditioning system of a cabin of an air or rail transport vehicle
The invention relates to a loop (40) for extracting water from an air conditioning system of a cabin (5) of an air or rail transport vehicle comprising an air cycle turbine engine (20), the loop comprising: a condenser (41); a three-dimensional mesh grid (45) housed in an outlet box (42) of the condenser and configured to be able to capture water droplets in a stream of moist air condensed by the condenser; a water recovery unit (46) opening on the condenser outlet box (42) and arranged under the three-dimensional mesh grid (45) so as to be able to recover, by force of gravity, the water collected by the three-dimensional mesh grid (45); an air return pipe (44) linking the outlet box (42) to a supply interface for directly or indirectly supplying the turbine of the air conditioning system.
The invention relates to a system for cooling a fuel cell (10) of a transport vehicle, such as an aircraft, comprising a cooling heat exchanger (30) configured to be able to exchange heat between a loop (20) for cooling the cell and a channel for circulating dynamic air; a device (22, 23) for recovering water produced by the fuel cell; a tank (25) for storing recovered water; a device (50) for spraying water into the dynamic air channel (40) upstream of the heat exchanger (30); a computer (28) for controlling the amount of sprayed water as a function of a measurement representing the temperature of the fuel cell (10).
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
B64D 37/00 - Arrangements in connection with fuel supply for power plant
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
H01M 8/04992 - Processes for controlling fuel cells or fuel cell systems characterised by the implementation of mathematical or computational algorithms, e.g. feedback control loops, fuzzy logic, neural networks or artificial intelligence
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
60.
PROCESS FOR TREATING THE SURFACE OF A PART MADE OF ALUMINIUM OR ALUMINIUM ALLOY OR OF MAGNESIUM OR MAGNESIUM ALLOY
The invention relates to a method for the surface treatment of a part made from aluminum or aluminum alloy or from magnesium or magnesium alloy, comprising a step of treatment by oxidation of said part and a step of applying an aqueous composition to the surface of said part.
The invention relates to a heat exchanger that is configured to permit an exchange of heat between a first fluid and a second fluid that circulate in passage paths formed by plates (14a, 14b) and fins (16a, 16b) of the heat exchanger, the fluids flowing in a multitude of passage channels (10) each consisting of a closed space (12) delimited by two adjacent plates and two adjacent fins, characterized in that each plate extends along a non-planar surface following at least one oscillating curve, and each fin further following at least one second oscillating curve along at least one second main direction, in such a way that each passage path allows the fluid to flow in the closed space along a fluid direction defined by a generatrix that is a combination at least of the first oscillating curve and the second oscillating curve.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28F 3/06 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being attachable to the element
64.
System and method for cooling a fluid of a lubrication or cooling circuit of a drive unit of an aircraft, and aircraft propulsion engine provided with such a cooling system
The invention relates to a system for cooling a fluid of a circuit (20) for lubricating a propulsion engine (10) of an aircraft, the engine comprising a nacelle (11) which extends in a longitudinal direction (X) between an air inlet opening (12) and an ejection nozzle (13), a turbomachine (14) having a casing (15) secured inside said nacelle by rectifier arms (16), and a fan (17) arranged at said air inlet opening (12) of said nacelle, upstream of said turbomachine (14), and designed to be able to generate a primary air flow feeding said turbomachine and a secondary air flow feeding a channel, referred to as a secondary channel (18), formed between said nacelle (11) and said casing (15) of said turbomachine, characterized in that said cooling system comprises a skin exchanger (30) which is arranged on an inner wall of said nacelle (11), longitudinally between said air inlet opening (12) of said nacelle and said rectifier arms (16), said skin exchanger being in fluid communication with said fluid circuit and designed to be able to provide heat exchanges between said lubricating fluid and the air flowing through said secondary channel.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
65.
AIR-CONDITIONING SYSTEM FOR A CABIN OF AN AIR OR RAIL TRANSPORT VEHICLE USING A PNEUMATIC AND THERMAL AIR SOURCE SEPARATE FROM THE AIR-CONDITIONING SOURCE
The invention relates to an air-conditioning system for a cabin (10) of an aircraft (80) comprising a bleed air source (12); a dynamic air circulation channel (13); a network of ducts and control valves; an air-cycle turbomachine comprising at least one compressor (3) and a power turbine (4) mechanically connected to one another; at least one primary heat exchanger (PHX) housed in said channel (13), characterised in that said network of ducts comprises a thermal power duct (53) suitable for being able to fluidly connect, upon operating at least one control valve (25, 21), said air outlet (4b) of said power turbine (4) and said dynamic air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a source of thermal energy for said dynamic air feeding said primary circuit of said primary exchanger (PHX).
The invention relates to a method for supplying air at a controlled temperature to a cabin of a surface vehicle in which at least one air cycle device is used, comprising at least one motorized turbocompressor. The air inlet of the turbine is arranged to receive a compressed airflow from the compressor. At least one exchanger is interposed between the air outlet of the compressor and the air inlet of the turbine. The air inlet of the compressor is arranged to receive air at a pressure greater than or equal to atmospheric pressure. The invention likewise relates to a surface vehicle comprising at least one such air cycle device.
A fluid flow control valve includes a valve body, a closing member arranged in the valve body and configured so that it can have at least one first position, called the open position, in which it allows the flow of fluid to flow freely in the valve body, and at least one second position, called the closed position, in which it prevents the fluid flow from flowing in the valve body between the fluid inlet and the fluid outlet, an electric actuator of the closing member that is suitable for being able to control the position of the closing member in the valve body, characterized in that the electric actuator is arranged in the valve body so that it can be cooled by the flow of fluid flowing in the valve body.
F16K 5/04 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having cylindrical surfacesPackings therefor
F16K 31/06 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a magnet
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B61D 27/00 - Heating, cooling, ventilating, or air-conditioning
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
68.
Air sampling system equipped with an overpressure valve
The invention relates to an air bleed system comprising an air bleed port provided on an engine of an aircraft, an air supply pipe, a pressure sensor, a pressure relief valve mounted in said air supply pipe, characterized in that said pressure relief valve comprises: a valve body (11); a closure member (121) pivotally mounted in said air circulation duct; and an air discharge channel (13) passing through said valve body (11); at least one air discharge opening (15) formed on said upstream face of said closure member (121) and at least one air evacuation opening (19) which opens out to the outside of the air circulation duct.
F16K 5/04 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having cylindrical surfacesPackings therefor
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F16K 11/085 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only taps or cocks with cylindrical plug
69.
METHOD FOR MANUFACTURING A FIRE-RESISTANT PART OF AN AIR CONDITIONING SYSTEM AND PART PRODUCED BY SUCH A METHOD
Method for manufacturing a fire-resistant part of an air conditioning system (9) for an air or rail transport vehicle (8), characterised in that it comprises at least the following steps: a step (10) of obtaining a part comprising at least one aluminium alloy surface portion, and a step (20) of treating the aluminium alloy surface portion by means of micro-arc oxidation in order to produce a ceramic coating on the surface portion.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
C23C 4/02 - Pretreatment of the material to be coated, e.g. for coating on selected surface areas
C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
C23C 24/04 - Impact or kinetic deposition of particles
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
Air conditioning system for a cabin of an air or rail transportation vehicle comprising a pneumatic turbomachine comprising at least one compressor and at least one turbine (126) connected by a mechanical shaft extending along an axis, referred to as the turbomachine axis (132), the turbine comprising an air inlet and an air outlet, and a water extraction loop comprising a heater (110), a condenser (112), and a water separator (114), fluidly arranged between an air outlet of the compressor and the air inlet of the turbine (126), configured to dry the air supplied to the turbine (126), characterized in that the heater (110), the condenser (112) and the water separator (114) are arranged in a series on the axis or about the axis (132) of the turbomachine, forming the air inlet of the turbine (126).
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B61D 27/00 - Heating, cooling, ventilating, or air-conditioning
71.
HEAT EXCHANGER OF AN AIR-CONDITIONING SYSTEM OF A CABIN OF AN AIRCRAFT, AND SYSTEM COMPRISING SUCH A HEAT EXCHANGER
Heat exchanger of an air-conditioning system of a cabin of a transport vehicle, comprising: a primary circuit supplied by a first air flow (169), a secondary circuit supplied by a second air flow (168), a casing (161) defining an air-circulation enclosure (162), a primary circuit inlet box (164) allowing entry into said air-circulation enclosure, and a primary circuit outlet box (165) allowing exit from the air-circulation enclosure, characterized in that said inlet box (164) is mounted removably on said casing (161), and in that it houses a three-dimensional structure (163) forming a catalytic and/or adsorbent support for treating the air of said primary circuit, and a means for distributing said first air flow into said heat-exchange matrix.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
Air conditioning system for an aircraft cabin, comprising a primary exchanger (14) configured to cool collected air (12) originating from at least one aircraft compressor, a pre-compressor (18), an intermediate exchanger (20), a main compressor (22) configured to compress the collected pre-compressed air, a main exchanger (28) configured to cool the collected compressed air, and a water extraction loop, characterised in that the system comprises a pipe (108) for recovering at least part of the air from the cabin after it has passed through the cabin, and pipes for circulating the recovered air which are configured such that the recovered air consecutively passes through a secondary exchanger (34), the recovered air forming a first cold source for cooling the collected air again, a heat exchanger (20), the recovered air forming a second cold source for cooling the collected air, a turbine (48) for recovering energy, the recovered air forming an energy source.
The invention relates to a method and a system for monitoring the state of a heat exchanger (17) in an air circuit (5) of an aircraft (7), the heat exchanger being intended to cool the air extracted from a main hot air source of the aircraft, the system comprising: - an acquisition module (11) configured to acquire temperature measurements taken by a probe arranged at an outlet of the heat exchanger, the acquisition being carried out when the air circuit is supplied by a secondary hot air source downstream of the heat exchanger and the main hot air source is disconnected, - a processor (9) configured to select a relevant temperature measurement from among the temperature measurements and to detect a possible leak in the heat exchanger (17) by comparing the relevant temperature measurement with a predetermined alert threshold.
The invention relates to an assembly of heat exchangers comprising a dynamic air flow channel (14) extending in a longitudinal direction and characterised in that it comprises at least two heat exchangers (12a, 12b) which are separated and adjacent in a transverse direction perpendicular to the longitudinal direction, arranged in the dynamic air flow channel (14), and configured so that the dynamic air passing through the channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through the heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured to have a fluid to be cooled passing through it, forming a hot pass (20a, 20b), and an air passage formed between the heat exchangers forming a thermally insulating air gap (18) between the heat exchangers (12a, 12b), the air passage extending in the longitudinal direction of the dynamic air flow channel (14).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
75.
AIRCRAFT CABIN ELECTRICAL AIR CONDITIONING SYSTEM COMPRISING A MOTORIZED COMPRESSOR AND AN AIR CYCLE TURBOMACHINE
The invention relates to an electrical air conditioning system for air-conditioning a cabin (10) of an aircraft comprising a source (11) of fresh air, a dynamic air circulation duct (12), a motorized compressor (13) comprising an air inlet connected to said source of fresh air, and an air outlet connected to a primary cooling exchanger (PHx) housed in said dynamic air duct; an air cycle turbomachine (14) comprising at least a first compressor (15) and a first turbine (17) which are mechanically coupled to one another, said first compressor comprising an air inlet which can be connected either to said primary cooling exchanger (PHx) or to said source (11) of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine (17) comprising an air inlet which can be connected either to a discharge port (54) for discharging stale air from said cabin or to said main cooling exchanger (MHx), and an air outlet which can be connected either to said cabin (10) or to an air injector (52) opening into said dynamic air duct.
A method for manufacturing an electrically conductive composite material includes obtaining a composite material which includes a thermoplastic matrix and short carbon fibers and is free of carbon nanotubes, preheating a furnace until a predetermined target temperature is reached, inserting the composite material into the preheated furnace once the target temperature has been reached, and heating the composite material in the furnace at the predetermined target temperature which is kept constant for a predetermined duration.
H01B 1/24 - Conductive material dispersed in non-conductive organic material the conductive material comprising carbon-silicon compounds, carbon, or silicon
B29B 9/14 - Making granules characterised by structure or composition fibre-reinforced
B29C 45/00 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
C08G 65/40 - Macromolecular compounds obtained by reactions forming an ether link in the main chain of the macromolecule from hydroxy compounds or their metallic derivatives derived from phenols from phenols and other compounds
B29K 71/00 - Use of polyethers as moulding material
B29K 105/12 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of short lengths, e.g. chopped filaments, staple fibres or bristles
The invention relates to a regulator, configured to receive a stream of hot air carrying pneumatic power via an air inlet (12), to treat this hot air and to send the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising a reference pressure source and an air expansion device comprising a diaphragm (22), the diaphragm (22) being configured to control the flow rate of the hot air stream by comparing the pressure of said hot air stream with the reference pressure of the reference pressure source. The regulator is characterised in that it comprises an air intake (24) configured to receive a cold source, and a pipe (25) for guiding the cold source to the diaphragm (22), so that the cold source forms the reference pressure source and a source for cooling the diaphragm (22).
The invention relates to a regulator, configured to receive a hot air flow via an air inlet (12), to treat this hot air and to transmit the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising at least one temperature-sensitive electrical and/or mechanical element (36, 37), and a regulator body (100). The regulator is characterized in that the regulator body is composed of a heat-conducting hollow enclosure (28) at least partially surrounding a duct (22) for transporting the hot air flow, said cavity being at least partially filled with a metal mesh produced by additive manufacturing that allows the cooling air to circulate, and in that the temperature-sensitive electrical and/or mechanical element (36, 37) is arranged in, or in contact with, the regulator so as to be cooled by the cooling air by thermal conduction.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
The invention concerns an aircraft cabin air conditioning system, comprising two motorised turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as the water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, referred to as the cooling turbine (16b), helping cool the air. The air conditioning system comprises a network of pipes and associated valves, connected to the common outlet (24) of the compressors and supplying, from the common outlet of the compressors: either the intake (160) of the water extraction turbine (16a), or the intake (164) of the cooling turbine (16b), bypassing the turbine (16a) and the water extraction loop, or, directly, an outlet (60) of the air conditioning system, bypassing the cooling turbine (16b) and the water extraction turbine (16a).
Aircraft air conditioning system comprising a thermal management system supplied with air, referred to as pressurized air (12), by at least one compressor (14) of the aircraft, and supplied with non-pressurized flow air (206; 208) coming from at least one engine of the aircraft, and characterized in that the thermal management system comprises at least one pressurized-air/oil heat exchanger (20) configured to provide exchanges of heat between a stream of pressurized air (12) and a first oil circuit (26) allowing heat to be transferred from the pressurized air (12) to the oil of the first oil circuit (26), at least one oil/flow-air heat exchanger (22a, 22b, 22c, 22d) configured to provide exchanges of heat between a second oil circuit (28) and the flow air (206; 208) allowing the heat from said second oil circuit (26) to be transferred to the flow air (206; 208), at least one connecting circuit (30) connecting the first oil circuit (26) and said second oil circuit (28).
Air conditioning system for a cabin (10) of an aircraft, comprising: an air intake device; an air cycle turbomachine (12); at least one main cooling exchanger (16); a water extraction loop (30); a duct (26) for distributing water extracted by the extraction loop (30), characterised in that it further comprises means (40) for reheating the water extracted by the water extraction loop in order to be able to atomise the water in a dynamic air channel (22) which supplies the main exchanger (16).
Exchanger (16) for cooling warm primary air with cool secondary air, comprising: a plurality of circulation channels for the secondary air (80); a plurality of circulation channels for the primary air, characterised in that it further comprises: water circulation channels (83) which each extend adjacent to a secondary channel (80); micro-perforated hollow bars (63) for atomising water, which each extend adjacent to a primary channel (60) and which are connected in fluid terms to the micro-perforated hollow bars in order to be able to reheat the water by interacting with the primary air before atomisation in the flow of primary air at the inlet of the exchanger.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
83.
Fluid flow control valve equipped with a conical flap and system comprising such valve
A valve for controlling a fluid flow includes a valve body, a shutter component configured to be able to transition from an open position allowing the circulation of fluid, to a closed position preventing the circulation of fluid. The component is characterized in that it includes a fixed conical support integral with the valve body, a conjugate conical flap rotationally movable relative to the fixed support, and fluid passage apertures respectively arranged in the conical flap and in the fixed support, and an actuator of the shutter component adapted to be able to control the position of the shutter component.
F16K 3/34 - Arrangements for modifying the way in which the rate of flow varies during the actuation of the valve
F16K 3/22 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with sealing faces shaped as surfaces of solids of revolution
F16K 39/04 - Devices for relieving the pressure on the sealing faces for sliding valves
F16K 3/18 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with flat sealing facesPackings therefor with special arrangements for separating the sealing faces or for pressing them together by movement of the closure members
B61D 27/00 - Heating, cooling, ventilating, or air-conditioning
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
84.
HEAT EXCHANGER AND SYSTEM FOR COOLING A FLUID COMPRISING SUCH A HEAT EXCHANGER
A tubular heat exchanger (10) comprising: a fluid circulation chamber (20) intended to be supplied with a first fluid, referred to as outer fluid, brought to a first temperature, a heat exchange matrix (30) housed in said circulation chamber and formed by a plurality of heat exchange tubes (31) each comprising at least one pair of ducts (32; 33) nested one inside the other, extending along a direction, referred to as longitudinal direction, and defining: a channel for the circulation of a fluid, referred to as inner channel (32c; 33c), suitable for being able to to supplied with a second fluid, referred to as inner fluid, brought to a second temperature, and a channel for the circulation of a fluid, referred to as intermediate channel (32d, 33d), and suitable for being able to be supplied with a third fluid, referred to as intermediate fluid, brought to a third temperature, different from said first temperature.
F28D 7/10 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
F22B 37/12 - Forms of water tubes, e.g. of varying cross-section
85.
LOOP FOR EXTRACTING WATER FROM AN AIR CONDITIONING SYSTEM OF A CABIN OF AN AIR OR RAIL TRANSPORT VEHICLE
The invention concerns a loop (40) for extracting water from an air conditioning system of a cabin (5) of an air or rail transport vehicle comprising an air cycle turbine engine (20), the loop comprising: a condenser (41); a three-dimensional mesh grid (45) housed in an outlet box (42) of the condenser and configured to be able to capture the water droplets in a stream of moist air condensed by the condenser; a water recovery unit (46) opening on the condenser outlet box (42) and arranged under the three-dimensional mesh grid (45) so as to be able to recover, by force of gravity, the water collected by the three-dimensional mesh grid (45); an air return pipe (44) linking the outlet box (42) to a supply interface for directly or indirectly supplying the turbine of the air conditioning system.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
86.
COMPOSITION FOR CHROMIUM PLATING A SUBSTRATE AND CHROMIUM PLATING PROCESS USING SUCH A COMPOSITION
The invention relates to an aqueous composition for the electrolytic deposition of a chromium coating on the surface of a substrate, which has a pH of between 0 and 1 and which contains a trivalent chromium salt, glycine, an alkali metal salt, an aluminium salt and, optionally, an ammonium salt. The chromium plating process according to the invention comprises the immersion of the substrate to be treated in this composition and the application of a current between this substrate and an anode. This process makes it possible to form a high-quality chromium coating on the entire surface of the substrate.
The invention relates to a distributor for a turbomachine radial turbine, comprising an annular grill (26) extending around a central axis (10) and comprising a plurality of blades (31) with variable pitch, defining among them an air passage section, characterized in that each blade is rotatably mounted around a pivot shaft (32), itself moveable along a translation direction, comprising at least one radial component, such that said blade can, upon actuation of control means (40), be pivoted around the pivot shaft and/or moved in relation to the central axis along said translation direction so as to be able to modify the air passage cross-section by respectively controlling the metal angle (α3) and the radial spacing (ΔR).
The invention relates to a device (30) for cooling heat-sensitive control members (29) of a pneumatic or electropneumatic valve (20), comprising a containment casing (31) designed to contain said control members (29); a fresh air inlet (32) in said containment casing (31); an air outlet (33) of said containment casing, provided with a ventilation air tube (34) that comprises: an air acceleration column (35) which puts into fluidic communication said containment casing (31) and the air outlet (33); a primary supply (37) for supplying the acceleration column (35) with primary air; a secondary supply (38) for supplying the acceleration column (35) with secondary air, provided in said containment casing (31) such that the primary air can drive and accelerate the secondary air in the direction of the air outlet so as to produce forced air ventilation in said containment casing (31) between the air inlet (32) and the air outlet (33).
F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
F02C 6/06 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F16K 49/00 - Means in or on valves for heating or cooling
F04F 5/20 - Jet pumps, i.e. devices in which fluid flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids for evacuating
89.
SYSTEM AND METHOD FOR COOLING A FLUID OF A LUBRICATION OR COOLING CIRCUIT OF A DRIVE UNIT OF AN AIRCRAFT AND AIRCRAFT PROPULSION ENGINE PROVIDED WITH SUCH A COOLING SYSTEM
The invention relates to a system for cooling a fluid of a lubrication circuit (20) of a propulsion engine (10) of an aircraft comprising a nacelle (11) which extends in a longitudinal direction (X) between an air inlet (12) and an ejection nozzle (13), a turbomachine (14) comprising a casing (15) attached to the inside of said nacelle by straightening arms (16), and a blower (17) which is arranged at said air inlet (12) of said nacelle, upstream of said turbomachine (14), and configured to be able to generate a flow of primary air supplying said turbomachine and a flow of secondary air supplying a channel, referred to as a secondary channel (18), formed between said nacelle (11) and said casing (15) of said turbomachine, characterised in that said cooling system comprises a skin exchanger (30) arranged on a wall inside said nacelle (11), longitudinally between said air inlet (12) of said nacelle and said straightening arms (16), said skin exchanger being in fluid communication with said lubrication circuit and configured to be able to ensure heat exchanges between said lubrication fluid and the air circulating in said secondary channel.
The invention relates to an aerodynamic radial bearing device with sheets, comprising a cylindrical sleeve (10) extending along a longitudinal direction, and having an inner surface (11) which defines a central bore, characterised in that it further comprises: at least one longitudinal notch (40, 50, 60) formed in said cylindrical sleeve and opening radially into said central bore; a first peripheral inner lining, referred to as corrugated lining, comprising at least one metal sheet provided with radial projections, referred to as corrugated sheet (22, 23, 24), each corrugated sheet having, at each end, a radial tongue, referred to as corrugated radial tongue (22a, 22b, 23a, 23b, 24a, 24b), freely housed in a longitudinal notch (40, 50, 60); a second peripheral inner lining, referred to as upper lining, comprising at least one metal sheet, referred to as upper sheet (32, 33, 34), each upper sheet having, at each end, a radial tongue, referred to as upper radial tongue (32a, 32b, 33a, 33a, 33b, 34a, 34b), freely housed in a longitudinal notch (40, 50, 60).
The invention relates to a process for treating the surface of a part made of aluminium or aluminium alloy or of magnesium or magnesium alloy, comprising a step of treating said part by oxidation and a step of applying an aqueous composition to the surface of said part.
C25D 11/30 - Anodisation of magnesium or alloys based thereon
C23C 22/44 - Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH < 6 containing molybdates, tungstates or vanadates containing also fluorides or complex fluorides
The invention relates to a an air-conditioning system for an aircraft, comprising a turbomachine comprising at least one radial turbine and a compressor, said radial turbine extending along a central axis (10) and comprising a wheel (20) provided with vanes (21) which is mounted such that it can rotate about said central axis (10), a distributor (30) arranged on the periphery of said wheel (20), comprising a plurality of variable-pitch blades (31) arranged around said central axis (10), and a volute (12) comprising an air inlet (12a) and an air outlet (12b) opening up towards said plurality of variable-pitch blades (31), characterised in that said variable-pitch blades (31) are arranged around said central axis (10) between two distributor housing walls (11a, 11b), defining a section between each other for the passage of the air from said distributor, each variable-pitch blade (31) also comprising means for the axial movement of the blade between the two housing walls (11a, 11b).
The invention relates to an air sampling system comprising an air sampling port created on an engine of the aircraft, an air supply duct, a pressure sensor, an overpressure valve mounted in said air supply duct, characterized in that said overpressure valve comprises: a valve body (11), a closure member (121) mounted so as to be able to pivot in said air circulation duct; and an air discharge duct (13) passing through said valve body (11); at least one air discharge orifice (15) formed on said upstream face of said closure member (121) and at least one air egress orifice (19) that opens outside the air circulation duct.
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
F16K 11/052 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only lift valves with pivoted closure members, e.g. butterfly valves
F16K 5/04 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having cylindrical surfacesPackings therefor
F16K 11/085 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only taps or cocks with cylindrical plug
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
94.
Method for coating a turbomachine part with a self-lubricating coating and part coated by said method
F16C 32/06 - Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure air source.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
96.
Torque motor including a winding support for stator windings and method for assembling a torque motor of this type
The invention relates to a torque motor comprising a stator and a rotor that extend along a common central axis. The stator includes an integral magnetic body and at least one pair of radial teeth that extend along the central axis and define slots for receiving stator windings, and at least one permanent magnet supported by the integral magnetic body. The torque motor also includes a winding support for the stator windings that has a hollow body that extends along the central axis and that delimits a chamber for receiving the rotor, and cavities for receiving the stator windings. In this way, the stator windings are integrated in the stator by the winding support, fitted with the stator windings, being axially inserted into the integral magnetic body.
H02K 3/30 - Windings characterised by the insulating material
H02K 3/48 - Fastening of windings on the stator or rotor structure in slots
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 15/04 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings prior to their mounting into the machines
H02K 3/52 - Fastening salient pole windings or connections thereto
97.
Aircraft cabin environmental control system and method and aircraft equipped with such control system
The invention relates to a system for environmental control of an aircraft cabin (5), comprising a device for bleeding compressed air from at least one aircraft engine; an air cycle turbine engine (20) comprising at least one supercharger (21) connected to said device for bleeding compressed air by an air bleed duct (7) and a turbine (22) connected to the cabin (5) by a cabin inlet duct (8) in order to be able to supply said cabin with air at a controlled pressure and temperature, characterised in that it further comprises: stationary blading (23) which has a variable injection cross section and is mounted on said turbine (22) of said air cycle turbine engine (20) so as to be able to modify, on command, the flow rate and/or the pressure of air supplying an air inlet of said turbine (22); and a second supercharger (22) which is mounted on said air cycle turbine engine (20) and is connected to a device for bleeding outside air and to said bleed duct.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
Disclosed is a method and a device for thermally controlling a plurality of cabins of a vehicle from a mixing chamber supplied with air from at least one air supply device of which at least the temperature is controlled, each cabin being supplied with air by a supply conduit specific to this cabin. At least one cabin is supplied with air at a temperature adjusted by at least one individual exchanger associated with the supply conduit specific to this cabin, in which a second circuit is supplied with a heat transfer fluid from at least one heat transfer fluid thermal regulation loop of the vehicle. Also disclosed is a vehicle provided with at least one thermal control device.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B60H 1/00 - Heating, cooling or ventilating devices
The invention relates to a method for supplying air at a controlled temperature to a cabin (10) of a land vehicle, in which use is made of at least one air cycle device comprising at least one motorized turbo compressor. The air inlet (16) of the turbine (14) is arranged to receive a flow of compressed air from the compressor (15). At least one exchanger (20, 32) is interposed between the air outlet (19) of the compressor (15) and the air inlet (16) of the turbine (14). The air inlet (18) of the compressor (15) is arranged to receive air at a pressure greater than or equal to atmospheric pressure. The invention also relates to a land vehicle comprising at least one such air cycle device.
The invention relates to an aircraft electrical network comprising an electrical device (28, 29) for protecting an outer surface of the aircraft from frost, which is suitable for being able to be supplied with power by a shared electrical power supply (24b, 24d, 24e) that is linked to an electric motor of a compressor of a thermal management device (25, 26, 27) via a switching device (37) to which an electrical frost protection device (28, 29) is also linked. If the altitude criteria of the aircraft are met, the switching device (37) is placed in a state in which the shared electrical power supply (24b, 24d, 24e) is electrically connected to at least one electrical frost protection device (28, 29). The invention extends to a method for distributing electricity for a shared electrical power supply on board an aircraft.
